KR20210048508A - Launch system - Google Patents

Abstract

According to at least one embodiment, there is provided a launch system including a carrier vehicle and at least one payload vehicle. The payload includes aerodynamic lift surfaces and a payload propulsion system designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at the desired altitude. The vehicle is configured to transport the at least one payload to at least a desired altitude, and further comprises a solid rocket propulsion system for propelling the launch system to a desired altitude. The vehicle is configured to provide a predetermined forward speed that correlates with the design subsonic cruising speed at the desired altitude. The vehicle is configured to release the payload relative to the vehicle at a desired altitude and a predetermined forward speed. The design subsonic cruising speed is less than 0.7 Mach number, and the target altitude is higher than 3 km.

Description

Launch system

The subject of the present disclosure relates to vehicles, in particular UAVs.

Unmanned Aerial Vehicles (UAVs) have been in use for many years, cover a variety of aircraft configurations and applications, and can be remotely controlled or autonomously controlled. These UAVs include fixed and rotating wing configurations, and uses, and may include intelligence, surveillance and reconnaissance, among others.

Some missions may optionally require aircraft configurations that provide subsonic cruising capabilities, including roaming, and in some cases at high altitude. High lift ratio aircraft configurations, and the high span to chord ratio for these aircraft configurations, can optimize performance at subsonic cruises and at high altitudes. On the other hand, these aircraft configurations are associated with low rates of ascent to these high altitudes.

According to a first aspect of the subject matter of the present disclosure, there is provided a launch system comprising a vehicle and at least one payload:

The payload comprises a payload propulsion system and aerodynamic lift surfaces designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;

The vehicle is configured to transport the at least one payload to at least the desired altitude, further comprising a solid rocket propulsion system for propelling the launch system to the desired altitude;

The vehicle is configured to provide a predetermined advancing speed at the desired altitude, the predetermined advancing speed being correlated with the design subsonic cruising speed;

The vehicle is configured to release the payload relative to the vehicle at the desired altitude and the predetermined forward speed;

The design subsonic cruising speed is less than 0.7 Mach number;

The target altitude is higher than 3 km.

According to a variant of the first aspect of the present disclosure, there is provided a launch system comprising a vehicle and at least one payload:

The payload comprises aerodynamically floating surfaces and an onboard propulsion system designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;

The vehicle is configured to transport the at least one payload to at least the desired altitude, further comprising a solid rocket propulsion system for propelling the launch system to the desired altitude;

The vehicle is configured to provide a predetermined advancing speed at the desired altitude, the predetermined advancing speed being correlated with the design subsonic cruising speed;

The vehicle is configured to release the payload relative to the vehicle at the desired altitude and the predetermined forward speed;

The design subsonic cruising speed is less than 0.7 Mach number;

The target altitude is as follows: 2 km; It is higher than any one of 1 km.

According to another variant of the first aspect of the present disclosure, there is provided a launch system comprising a vehicle and at least one payload:

The payload comprises a payload propulsion system and aerodynamic lift surfaces designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;

The vehicle is configured to transport the at least one payload to at least the desired altitude, further comprising a solid rocket propulsion system for propelling the launch system to the desired altitude;

The vehicle is configured to provide a predetermined advancing speed at the desired altitude, the predetermined advancing speed being correlated with the design subsonic cruising speed;

The vehicle is configured to release the payload relative to the vehicle at the desired altitude and the predetermined forward speed;

The design subsonic cruising speed is less than 0.7 Mach number;

The target altitude is as follows: 4 km; 5 km, 6 km; 7 km; It is higher than any one of more than 8km, 10km, 11km, 12km or 12km.

According to another variant of the first aspect of the present disclosure, there is provided a launch system comprising a vehicle and at least one payload:

The payload comprises an onboard propulsion system designed to provide vector powered flight at a design subsonic cruising speed to the payload at a desired altitude;

The vehicle is configured to transport the at least one payload to at least the desired altitude, further comprising a solid rocket propulsion system for propelling the launch system to the desired altitude;

The vehicle is configured to provide a predetermined advancing speed at the desired altitude, the predetermined advancing speed being correlated with the design subsonic cruising speed;

The vehicle is configured to release the payload relative to the vehicle at the desired altitude and at the predetermined forward speed.

For example, the design subsonic cruising speed is: 0.7M; 0.65M; 0.6M; 0.5M; 0.45M; 0.4M; 0.35M; 0.3M; 0.25M; Any one of 0.2M is low and/or; The target altitude is as follows: 1km, 2km, 3km, 4km; 5 km, 6 km; 7 km; It is higher than any one of more than 8km, 10km, 11km, 12km or 12km.

According to at least one of the aforementioned first aspect of the present disclosure subject, or of the aforementioned variations of the first aspect, the firing system may have one or more of the following features in any combination: for example, at least In some examples, the predetermined advance speed is a subsonic speed, and the predetermined advance speed is between zero and ±0.3 Mach of the maximum design subsonic cruising speed.

Additionally or alternatively, for example, in at least some examples, the payload is deployable between a stowed configuration and a deployed configuration, the payload being transported by the carrier and the containment. Configuration, wherein after the release the payload is deployed in the deployed configuration, the payload being designed for the aerodynamic power flight at the design subsonic cruising speed when in the deployed configuration. For example, the mounting body is reversibly deployable between the storage configuration and the deployment configuration.

Additionally or alternatively, for example, the lift ratio of the payload in the deployed configuration is at least 8, or optionally at least 9, or as a further option is 10, or as an additional option is greater than 10.

Additionally or alternatively, for example, the payload comprises a fuselage, the aerodynamic floating surfaces in the containment configuration have respective spans aligned with the fuselage, and in the deployed configuration the aerodynamic floating surfaces are the Each span has an angular relationship to the fuselage that allows the creation of aerodynamic lift at the design subsonic cruising speed.

Additionally or alternatively, for example, the payload cannot itself reach the desired altitude without the vehicle.

Additionally or alternatively, for example, there is no rocket motor system in the payload, or the onboard propulsion system itself is unable to allow the payload to reach the desired altitude, or the onboard propulsion system itself It is not possible to enable the payload to reach the desired altitude within a time period of less than 60 seconds; Or, the onboard propulsion system cannot itself enable the payload to reach the desired altitude within a time period of less than 2 minutes.

Additionally or alternatively, for example, the rocket propulsion system comprises at least one solid rocket motor and a solid propellant configured to propel the launch system to the desired altitude. For example, the solid state rocket motor provides an ISP in the range of about 180 seconds to about 250 seconds, and optionally in the range of about 180 seconds to about 200 seconds, and optionally in the range of about 180 seconds to about 220 seconds.

Additionally or alternatively, for example, the firing system is designed to reach a maximum speed below the desired altitude, the maximum speed being higher than the design subsonic cruising speed. For example, the payload cannot reach the maximum speed by itself without the carrier.

Additionally or alternatively, for example, the maximum speed is at least 1.5 times the design subsonic cruising speed, at least twice the design subsonic cruising speed, at least 3 times the design subsonic cruising speed, At least 4 times, at least 5 times the design subsonic cruising speed, or more than 5 times the design subsonic cruising speed.

Additionally or alternatively, for example, the payload is configured to provide a first average climb rate in the absence of the vehicle, and the launch system is designed to reach a second average climb rate below the desired altitude. However, the second average rate of increase is greater than the first average rate of increase. For example, the payload cannot reach the second ascent rate, which has proven itself.

Additionally or alternatively, for example, the second rate of increase may be: at least twice the first average rate of increase; At least 5 times the first average rate of increase; It is any one of at least 10 times the said 1st average increase rate.

Additionally or alternatively, for example, the desired altitude is: at least 5 km; At least 10 km; It may be any one of at least 12 km.

Additionally or alternatively, for example, the design subsonic cruising speed may be: 0.65M; 0.6M; 0.5M; 0.45M; 0.4M; 0.35M; 0.3M; 0.25M; It is less than any one of 0.2M.

Additionally or alternatively, for example, the onboard propulsion system comprises at least one of a fuel combustion engine and an electric motor operably coupled to a rotor, and optionally the rotor is a propeller. For example, the rotor is a propeller, and the propeller is a reversibly pivotable (or collapsible/unfoldable) propeller blade between a propeller containment configuration (or a folded configuration) and a propeller propulsion configuration (or an unfolded configuration). Includes them.

Additionally or alternatively, for example, the vehicle comprises a propulsion module comprising the solid rocket propulsion system, and a mounting module configured to transport the payload, wherein the propulsion module is detachably fastened to the mounting module. However, the disengagement of the engagement between the propulsion module and the mounting module enables the mounting body to be released from the mounting module at the desired altitude and the predetermined forward speed. For example, the mounting module includes a mounting bay for accommodating the payload while the payload is transported by the vehicle, the payload being releasable from the mounting module at the desired altitude and the predetermined advance speed. Do.

Additionally or alternatively, for example, the pushing module is configured to withdraw in a first predetermined target area.

Additionally or alternatively, for example, the mounting module is configured to withdraw in a second predetermined target area.

Additionally or alternatively, for example, the vehicle comprises a mounting bay configured to receive the payload, wherein the mounting bay will release the payload from the mounting bay at the desired altitude and the predetermined forward speed. It is openable to make it possible. For example, the vehicle is configured to recover in a predetermined third target area.

Additionally or alternatively, for example, the vehicle is further configured to transport the at least one payload to at least the desired range, wherein the vehicle comprises the desired altitude, the predetermined advance speed and the predetermined And is configured to release the payload relative to the transporter within a range.

Additionally or alternatively, for example, the predetermined forward speed is within a range between zero and the design subsonic cruising speed.

Additionally or alternatively, for example, the weight of the vehicle is in the range of 20% to 50% of the total weight of the launch system.

Additionally or alternatively, for example, the weight of the propulsion module is within the range of 20% to 50% of the total weight of the transport system 100 at launch.

Additionally or alternatively, for example, the vehicle is configured not to disengage the solid rocket propulsion system from the vehicle when releasing the payload relative to the vehicle at the desired altitude and the predetermined forward speed. .

Additionally or alternatively, for example, the vehicle does not have a parachute deployable to the payload when or after the payload is released with respect to the vehicle.

Additionally or alternatively, for example, the at least one payload comprises at least one sensor having a line of sight (LOS) having a positive elevation (relative to the horizon).

Additionally or alternatively, for example, the positive elevation is at least in a direction away from Earth when the payload is in aerodynamic-powered flight at the design subsonic cruising speed at the predetermined altitude.

Additionally or alternatively, for example, the elevation is within an elevation range between 0° and 90°.

Additionally or alternatively, for example, the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°.

Additionally or alternatively, for example, the FOV is configured to enable at least one of detecting, identifying and tracking an object. For example, the object is either satellites, aircraft, or anti-aircraft missiles.

Additionally or alternatively, for example, the LOS has an azimuth with respect to the payload, the azimuth angle being between 0° and ±180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between +90° and +180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between -90° and -180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or the visible spectrum.

Additionally or alternatively, for example, the firing system comprises an inertial platform, wherein the at least one sensor is mounted on the inertial platform.

According to a second aspect of the subject matter of the present disclosure, a method for firing a payload at a desired high velocity is provided:

(a) providing a launch system comprising the payload and the vehicle,

- The payload includes aerodynamic floating surfaces and an onboard propulsion system designed for aerodynamic power flight at a design subsonic cruising speed at a desired altitude;

- The vehicle is configured to transport the at least one payload to at least the desired altitude, further comprising a solid rocket propulsion system for propelling the launch system to the desired altitude;

- The vehicle is configured to provide a predetermined advancing speed at the desired altitude, the predetermined advancing speed being correlated with the design subsonic cruising speed;

- Said transport body is configured to release said payload from said mounting bay at said desired altitude and said predetermined forward speed;

- The design subsonic velocity is less than 0.7 Mach number;

- The desired altitude is higher than any one of the following: 5 km, or more than 4 km, or more than 3 km, or more than 2 km, or more than 1 km;

(b) firing the firing system and causing the firing system to reach the desired altitude and the predetermined forward speed;

(c) releasing the payload from the vehicle at the desired altitude and the predetermined forward speed;

(d) causing the payload to achieve aerodynamic power flight at the design subsonic cruising speed at least at the desired altitude.

According to alternative modified examples of the second aspect of the present disclosure, the desired altitude is instead higher than any one of 6km, 7km, 8km, 9km, 10km, 11km, 12, 15km.

According to the above-described second aspect of the present disclosure subject, or the above-described variations of the second aspect, the method may have one or more of the following features in any combination:

For example, the predetermined advance speed is a subsonic speed, and the predetermined advance speed is between zero and ±0.3 Mach number of the maximum design subsonic cruising speed.

Additionally or alternatively, for example, the payload is deployable between a containment configuration and a deployment configuration, and the step (d) of deploying the payload from the containment configuration to the deployed position after the release in step (c). And wherein the payload is designed for the aerodynamic power flight at the design subsonic cruising speed when in the deployed configuration.

Additionally or alternatively, for example, the payload comprises a fuselage, the aerodynamic floating surfaces in the containment configuration have respective spans aligned with the fuselage, and in the deployed configuration the aerodynamic floating surfaces are the Each span has an angular relationship to the fuselage that allows the creation of aerodynamic lift at the design subsonic cruising speed.

Additionally or alternatively, for example, the payload itself cannot reach the desired altitude without the vehicle, or the payload does not have a rocket motor system, or the onboard propulsion system itself is Or the onboard propulsion system is unable by itself to enable the payload to reach the desired altitude within a time period of less than 60 seconds; Or the onboard propulsion system itself is unable to allow the payload to reach the desired altitude within a time period of less than 2 minutes, or the rocket propulsion system is configured to propel the launch system to the desired altitude, At least one solid rocket motor and a solid propellant.

Additionally or alternatively, for example, in step (b) the firing system reaches a maximum speed below the desired altitude, the maximum speed being higher than the design subsonic cruising speed.

Additionally or alternatively, for example, the payload cannot reach the maximum speed by itself without the vehicle.

Additionally or alternatively, for example, the maximum speed may be: at least twice the design subsonic cruising speed; At least 5 times the design subsonic cruising speed; At least three times the design subsonic cruising speed, and at least four times the design subsonic cruising speed.

Additionally or alternatively, for example, the payload is configured to provide a first average ascent rate in the absence of the vehicle, and the launch system reaches a second average ascent rate below the desired altitude, wherein the second average The rate of increase is greater than the first average rate of increase. For example, the payload cannot reach the second ascent rate, which has proven itself. Additionally or alternatively, for example, the second rate of increase may be: at least twice the first average rate of increase; At least 5 times the first average rate of increase; It is any one of at least 10 times the said 1st average increase rate.

Additionally or alternatively, for example, the desired altitude is: at least 5 km; At least 10 km; It may be any one of at least 12 km.

Additionally or alternatively, for example, the design subsonic cruising speed is: 0.65M; 0.6M; 0.5M; 0.45M; 0.4M; 0.35M; 0.3M; 0.25M; It is less than any one of 0.2M.

Additionally or alternatively, for example, the onboard propulsion system comprises at least one of a fuel combustion engine and an electric motor operably coupled to the rotor, wherein the rotor is a propeller, and the propeller is a propeller containment configuration (or A reversibly pivotable (or collapsible/unfoldable) pivotable propeller blade between a folded configuration) and a propeller propulsion configuration (or an unfolded configuration), the method comprising the propeller when the payload is in the deployed configuration. Pivoting or unfolding wings from the propeller containment configuration to the propeller propulsion configuration.

Additionally or alternatively, for example, the vehicle comprises a propulsion module comprising the solid rocket propulsion system, and a mounting module configured to transport the payload, wherein the propulsion module is detachably fastened to the mounting module. And step (c) includes disengaging the propulsion module with respect to the mounting module, and then disengaging the mounting body from the mounting module at the desired altitude and the predetermined forward speed. For example, the method further comprises (e) recovering the pushing module in a first predetermined target area.

Additionally or alternatively, for example, step (e) comprises causing the propulsion module to follow a first trajectory to the first predetermined target area.

Additionally or alternatively, for example, the method further comprises (f) retrieving the mounting module in a second predetermined target area. For example, step (f) includes causing the mounting module to follow a second trajectory to the second predetermined target area.

Additionally or alternatively, for example, the vehicle comprises an openable mounting bay configured to receive the payload, wherein step (c) comprises opening the mounting bay and the desired altitude and the predetermined advancement. And releasing the payload from the mounting bay at speed. For example, the method further comprises (g) recovering the vehicle in a third predetermined target area. For example, step (g) includes causing the vehicle to follow a third trajectory to the third predetermined target area.

Additionally or alternatively, for example, step (b) further comprises bringing the firing system to a predetermined range, step (c) comprising the desired altitude, the predetermined advance speed and the predetermined And releasing the payload from the carrier within a range.

Additionally or alternatively, for example, the predetermined forward speed is between zero and the design subsonic cruising speed.

Additionally or alternatively, for example, the method further comprises step (h), wherein step (h) is:

- Reversing the deployment, wherein the payload is reduced from the deployment configuration to the containment configuration;

- And dropping the aerodynamic floating surfaces.

For example, step (h) is implemented just before the accretion of the payload on the ground at the end of the mission.

Additionally or alternatively, for example, the vehicle does not disengage the solid rocket propulsion system from the vehicle when releasing the payload relative to the vehicle at the desired altitude and the predetermined forward speed.

Additionally or alternatively, no parachute is deployed with respect to the payload, for example when or after the payload is released with respect to the vehicle.

Additionally or alternatively, for example, the at least one payload comprises at least one sensor having a line of sight (LOS) and further comprising aligning the LOS with a positive elevation (relative to the horizon).

Additionally or alternatively, for example, the positive elevation is at least in a direction away from Earth when the payload is in aerodynamic-powered flight at the design subsonic cruising speed at the predetermined elevation.

Additionally or alternatively, for example, the elevation is within an elevation range between 0° and 90°.

Additionally or alternatively, for example, the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°.

Additionally or alternatively, for example, the method further comprises using the at least one sensor for at least one of detecting, identifying and tracking an object. For example, the object is either satellites, aircraft, or anti-aircraft missiles.

Additionally or alternatively, for example, the LOS is aligned along an azimuth with respect to the payload, the azimuth being between 0° and ±180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between +90° and +180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between -90° and -180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or the visible spectrum.

Additionally or alternatively, for example, the payload comprises an inertial platform, on which the at least one sensor is mounted.

According to a third aspect of the subject matter of the present disclosure, there is provided a launch system comprising a vehicle and at least one payload:

The payload includes aerodynamically floating surfaces and an onboard propulsion system designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;

The vehicle is configured to transport the at least one payload, the vehicle further comprising a solid rocket propulsion system for propelling the launch system while transporting the at least one payload;

The vehicle is configured to release the payload relative to the vehicle at a predetermined altitude;

The at least one payload includes at least one sensor having a line of sight (LOS) having a positive elevation (relative to the horizon).

For example, the positive elevation is at least in a direction away from Earth when the payload is in aerodynamic-powered flight at the design subsonic cruising speed at the predetermined elevation.

Additionally or alternatively, for example, the elevation is within an elevation range between 0° and 90°.

Additionally or alternatively, for example, the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°.

Additionally or alternatively, for example, the FOV is configured to enable at least one of detecting, identifying and tracking an object. For example, the object is either satellites, aircraft, or anti-aircraft missiles.

Additionally or alternatively, for example, the LOS has an azimuth with respect to the payload, the azimuth angle being between 0° and ±180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between +90° and +180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between -90° and -180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or the visible spectrum.

Additionally or alternatively, for example, the firing system comprises an inertial platform, on which the at least one sensor is mounted.

According to a fourth aspect of the present disclosure, there is provided a method for firing a payload at a desired high velocity:

(a) Providing a launch system comprising the payload and the vehicle,

- The payload includes aerodynamically floating surfaces and an onboard propulsion system designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;

- The vehicle is configured to transport the at least one payload, the vehicle further comprising a solid rocket propulsion system for propelling the launch system while transporting the at least one payload;

- The vehicle is configured to release the payload relative to the vehicle at a predetermined altitude;

- Providing the firing system, wherein the at least one payload comprises at least one sensor having a line of sight (LOS);

(b) Firing the firing system and bringing the firing system to the desired altitude;

(c) Releasing the payload from the transport at the desired altitude;

(d) Causing the payload to achieve aerodynamically powered flight at the design subsonic cruising speed;

(e) Aligning the LOS with a positive elevation (relative to the horizon).

For example, the positive elevation is at least in a direction away from Earth when the payload is in aerodynamic-powered flight at the design subsonic cruising speed at the predetermined elevation.

Additionally or alternatively, for example, the elevation is within an elevation range between 0° and 90°.

Additionally or alternatively, for example, the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°.

Additionally or alternatively, for example, the method further comprises using the at least one sensor for at least one of detecting, identifying and tracking an object. For example, the object is either satellites, aircraft, or anti-aircraft missiles.

Additionally or alternatively, for example, the LOS is aligned along an azimuth with respect to the payload, the azimuth being between 0° and ±180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between +90° and +180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the azimuth angle is between -90° and -180° with respect to the longitudinal axis of the payload.

Additionally or alternatively, for example, the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or the visible spectrum.

Additionally or alternatively, for example, the payload comprises an inertial platform, on which the at least one sensor is mounted.

At least an exemplary feature of the subject matter of the present disclosure is that the launch system allows each payload to be deployed in the desired high posture much faster than any conventional system, and the payload itself is designed for subsonic cruising, while the payload can be realized by itself. It's much faster than it is. For example, this allows rapid deployment at high altitudes in emergency situations.

Another feature of at least one example of the subject of the present disclosure is that the launch system is an electric propulsion system (i.e., the propulsion system is driven by electric power only), and the payload itself is designed for subsonic cruising, while the electric propulsion system can realize itself. It makes it possible to deploy to the desired high posture much faster than is possible, thus also allowing the total electrical energy stored in the batteries of the electric propulsion system to be used for power flight at the desired altitude. For example, this allows rapid deployment at high altitudes in emergency situations.

In order to better understand the subject matter disclosed herein and to illustrate how this can be done in practice, examples will now be described by way of non-limiting example only with reference to the accompanying drawings, wherein:
1 is a side view of a firing system according to a first example of the subject matter of the present disclosure.
2 is a vertical cross-sectional view of the example of FIG. 1.
3 is a cross-sectional side view of the example of FIG. 2 taken along AA.
Fig. 4 is an isometric front/side/top view of the mounting body of the example of Fig. 2 in a storage configuration.
Fig. 5 is an isometric front/side/top view of the mounting body of the example of Fig. 2 in a deployed configuration.
6 schematically illustrates a method for operating the example of FIG. 1 in accordance with an aspect of the present disclosure.
7A schematically shows the change in thrust over time for the implementation of the example of FIGS. 1 and 6; 7B schematically shows the change in acceleration over time for the example implementation of FIGS. 1 and 6; 7C schematically shows the change in mass over time for the example implementation of FIGS. 1 and 6; 7D schematically illustrates the change in height over time for the implementation of the example of FIGS. 1 and 6.
8 schematically shows a change in height over a range for the implementation of the examples of FIGS. 1 and 6.
9 schematically shows the angle of elevation of the line of sight (LOS) of the sensor of the example of FIG. 1.
Fig. 10 schematically shows the azimuth angle of the LOS of the sensor of the example of Fig. 9;

Referring to FIGS. 1 and 2, a launch system according to a first example of the present disclosure collectively referred to as 100 includes a vehicle 200 and a payload 300. In alternative variants of this example, the launch system may include a vehicle and a plurality of payloads carried by the vehicle.

The launch system 100 is specifically configured to enable rapid deployment of the payload 300 through the vehicle 200, to a desired altitude (H), and optionally also along a predetermined range.

As will become more apparent herein, in these and other examples payload 300 not only provides the payload 300 with aerodynamic power flight at a design subsonic cruising speed at a desired altitude, but also at a lower altitude. For 300, it includes aerodynamically floating surfaces and onboard propulsion systems designed to enable aerodynamic-powered flight at subsonic speeds.

In addition, as will become clearer in the present specification, the vehicle 200 is configured to transport the payload 300 to at least a desired altitude (H), and propulsion of a solid rocket to propel the launch system 100 to a desired altitude. The system further includes. In addition, the vehicle 200 is configured to provide a predetermined forward speed at a desired altitude (H), and the determined forward speed has a correlation with the subsonic cruising speed of the payload 300. For example, the predetermined advance speed is correlated with the subsonic cruising speed of the payload 300 by a method in which the predetermined advance speed is within a range between zero and the design subsonic cruise speed of the payload 300.

When referring to the firing system 100, the term "forward speed" refers herein to the firing system 100 along a direction generally parallel to the longitudinal axis LA of the firing system 100. Represents the speed of; Alternatively, when referring to the firing system 100, the term "advance speed" refers herein to the speed of the firing system 100 along the trajectory direction of the firing system 100.

When referring to the vehicle 200, the term "advance speed" refers to the speed of the vehicle 200 along a direction generally parallel to the longitudinal axis LA2 of the vehicle 200 herein; Alternatively, when referring to the vehicle 200, the term "forward speed" refers to the speed of the vehicle 200 along the trajectory direction of the vehicle 200 in this specification.

When referring to the payload 300, the term "advance speed" refers to the speed of the payload 300 along a direction generally parallel to the longitudinal axis LA3 of the payload 300 herein; Alternatively, when referring to the payload 300, the term "forward speed" refers to the speed of the payload 300 along the trajectory direction of the payload 300 herein.

Further, the transport body 200 is configured to release the payload 300 relative to the transport body 200 at a desired altitude and the predetermined forward speed.

In at least some examples, the desired altitude may be above the cloud layer and/or any other suitable altitude, for example: at least 1 km, or at least 2 km, or at least 3 km, or at least 4 km, or at least 5 km, or at least 6 km, Or at least 7 km, or at least 8 km, or at least 9 km, or at least 10 km; Or at least 12 km, or at least 15 km.

Optionally, the predetermined range may be less than 1 km from the launch site, e.g. 0 km to 1 km, or alternatively the range may be within 1 km to 5 km from the launch site, e.g. not taking into account wind effects. have. Desired height

At least in this example, and as will be discussed in more detail below, the firing system 100 is typically fired vertically, or at a small angle relative to the vertical, in order to minimize the transition time to the desired altitude. For example, such an angle may be selected such that the trajectory of the vehicle 200 does not cause the vehicle to land at the launch base itself, such as after deployment of the payload 300.

In at least this example, the vehicle 200 is once configured as a rocket and includes a mounting module 210 and a propulsion module 250. However, in alternative variants of this example, the vehicle is instead a multistage rocket, or a single or multistage rocket capable of reaching the desired altitude and/or a predetermined range within a short period of time, thereby providing the acceleration required to do so. It can be configured as a mixed propulsion system medium. "Mixed propulsion system vehicle" means a medium having a propulsion system comprising, in addition to the solid rocket propulsion system, at least one additional propulsion system different from the solid rocket propulsion system.

In at least this example, the mounting module 210 includes a mounting bay 240 (also referred to herein as a mounting canister), and may be, for example, a longitudinal length L1 which may be about 70% of the longitudinal length L. ), and the propulsion module 250 has a longitudinal length L2, which may be, for example, about 30% of the longitudinal length L.

In at least this example, the mounting module 210 that includes the mounting body 300 together has approximately the same weight/mass as the propulsion module 250. Also, at least in these or other examples, the weight/mass of the payload 300 is, for example, about 85% of the weight/mass of the mounting module 210 combined with the payload 300.

In at least this example, vehicle 200 is configured as a controlled or guided missile capable of reaching a desired altitude and/or a predetermined range within a short period of time in a controlled manner.

However, in alternative variants of this example, the vehicle may instead be configured as a ballistic rocket capable of reaching a desired altitude and/or a predetermined range within a short period of time. For example, this configuration for the vehicle can optionally omit any control system for steering, other than providing aerodynamic stability, for example through aerodynamic ballasts.

In at least this example, the vehicle 200 has a body 205 of length L in the longitudinal direction, and the body has a nose 208 and a trailing obtuse 207. Also, at least in this example, the body 205 has a nominal circular cross section with an outer diameter DE along the length L. Alternatively, the body 205 has a non-circular cross-section along the length L and fits within a cylinder of the outer diameter DE.

The longitudinal axis LA2 of the vehicle 200 extends between the nose 208 and the trailing end 207 and is coaxial with the longitudinal axis LA of the launch system 100.

In this example, the vehicle 200 may be spin stabilized and/or includes a plurality, typically four, tail fins 215. In this example, the pins 215 are pivotably or otherwise retractably mounted to the propulsion module 250 and have a retractable or folded configuration prior to firing.

For example, the pins 215 are configured as wrap-around pins or flat pins that pivot about the body 205 in a very close proximity thereto in the initially folded configuration, and to provide stability. Pivoted in an unfolded configuration (eg, along a pivot axis parallel to the longitudinal axis LA2); Optionally these bent or flat pins are actuated to pivot about a suitable axis to provide the vehicle 200 with a control moment to enable its steering. In another example, the pins 215 are in the form of grid pins, pivoted very close thereto about the body 205 in the initially folded configuration, and to provide stability (e.g., longitudinal axis LA2). Pivoted in an unfolded configuration) along a pivot axis orthogonal to Optionally, these grid pins are actuated to pivot about a suitable axis to provide the vehicle 200 with a control moment to enable its steering.

In still other variations of these examples, some or all of the pins 215 are fixedly attached to the body 205.

In these and other examples, the firing system 100 may be fired through a suitable firing tube or a suitable firing rail (not shown).

Immediately after firing of the firing system 100, or vehicle 200, the pins 215 will be deployed in a radially elongated deployed configuration, as shown in FIGS. 1 and 2. In alternative variants of this and other examples, the pins may be in a fixed spatial relationship with respect to the vehicle 200.

The front end of the mounting module 210 includes the nose 208, and the trailing end 212 of the mounting module 210 is for mating with the complementary interface 255 at the front end of the propulsion module 250. It includes an interface 215. In at least this example, interface 215 and interface 255 are each held together in a suitable manner to allow selective separation of the mounting module 210 relative to the propulsion module 250, as will become more apparent herein. This is the type of flanges that are used. For example, the interface 215 and the interface 255 are respectively explosive bolts to enable selective disengagement of the mounting module 210 to the propulsion module 250 when the explosive bolts (not shown) are activated. It is in the form of flanges that are held together with them. Thereafter, the mounting module 210 may be separated from the propulsion module 250 in any suitable manner. For example, pistons or springs provided in one or the other of the mounting module 210 and the propulsion module 250 may be configured to push the mounting module 210 and the propulsion module 250 to each other. Additionally or alternatively, aerodynamic forces may be used to disengage the mounting module 210 relative to the propulsion module 250. For example, this aerodynamic force may include a difference in drag between the mounting module 250 and the propulsion module 250, thereby enabling separation of the propulsion module 250 with respect to the mounting module 210. have. To further support these aerodynamic forces, one or both of the mounting module 250 and the propulsion module 250 may be selectively deployed after disengagement in order to further differentiate the drag acting thereon. Brakes may be included.

In alternative variants of this example, or in other examples, the interface 215 and the system 255 are when the mounting module 210 and the propulsion module 250 reach at least a desired height and/or a predetermined range. Any other suitable arrangement may be included to allow the mounting module to be held together and to allow the mounting module to be selectively detachable relative to the propulsion module. For example, interface 215 and interface 255 may be held together through an explosive belt. In these or other examples, the mounting module 210 optionally has an outer shell formed as a plurality of segments that are separated from each other while still attached to the propulsion module 250, whereby the mounting body 300 is attached to the mounting module 210. Can be released from.

In at least this example, the payload 300 is deployable between a stowed configuration and a deployed configuration. In each containment configuration, and referring to FIG. 4, the payload 300 is compact, allowing the payload 300 to fit within the mounting bay 240 of the carrier 200 and otherwise be transported by the carrier. Have a composition. In particular, in this example in which the mounting bay has a nominal cylindrical shape, the mounting body 300 also has a respective containment configuration compactly fit within this nominal cylindrical shape. In each deployed configuration, and referring to FIG. 5, the payload 300 has an aerodynamic configuration that allows it to be operated in an aerodynamic flight mode when the payload 300 is released from the vehicle 200. In the aerodynamic flight mode, the payload 300 is designed for aerodynamic power flight described above at a design subsonic cruising speed when in the deployed configuration.

At least in this example, the payload is reversibly deployable between the storage configuration and the deployment configuration.

In at least this example, the mounting module 210 is configured to receive the mounting body 300 in its storage configuration therein, and the mounting module 210 includes an outer shell 215 defining a mounting bay 240 therein. do. In at least this example, and referring particularly to FIGS. 2 and 3, the mounting bay 240 defines an envelope E for which the payload 300 is suitable for its containment configuration. The mounting bay 240 also allows for reversible fixation of the payload 300 to the mounting module, in particular the outer shell 215 in a containment configuration, the acceleration and deceleration steps of the flight from the launch of the launch system 100. To support the payload 300 during, and after separation of the mounting module 210 from the propulsion module 250, to allow the payload 300 to be selectively released from the mounting module 210, in particular the mounting bay 215. It is composed.

In at least this example, the nose 208 is not an ogive or conical pointed shape, but has a hemispherical profile and is round. The rounded shape for the nose 208 provides additional interior space to the mounting bay 240 (for the same longitudinal length L1 for the mounting module 210) when compared to the ojave or conical pointed shape, It also provides higher drag when the firing system begins to decelerate after engine shutdown, as will become more apparent below. However, in alternative variations of this and other examples, the nose 208 may have an oblique or conical pointed shape. In yet other alternative variations of this and other examples, the nose 208 may have a blunt shape that can provide improved drag properties, for example compared to a round or ozive or pointed nose, and , This may facilitate deceleration of the launch system 100 prior to release of the payload 300.

In this example, the envelope E is a nominal cylindrical portion of diameter D1 that is smaller than the inner diameter DSI of the shell 215, abutting a nominal hemispherical portion E2 that is complementary to the inner hemispherical geometry of the nose 208. (E1) is included.

In at least this example, the propulsion module 250 may be configured with the launch system 100, in particular the vehicle 200, at a desired altitude (H) within a predetermined period of time (T) and optionally also to a predetermined range, and in advance. It comprises a solid rocket propulsion system 260 configured to provide motive power to the launch system 100, in particular the vehicle 200, in order to be able to reach the determined forward speed. In at least such an example, the propulsion system 260 may have a solid rocket motor 265 and a solid fuel propellant 268, a controller 270, as well as a desired altitude and/or a predetermined range after launch of the launch system 100 and And/or a suitable sensor system 269 configured to determine whether a time period T has been reached. For example, the solid state rocket motor 265 provides an ISP in the range of 180 seconds to 250 seconds, for example, up to about 200 seconds or up to about 220 seconds.

In at least these and other examples, the propulsion module 250 is a solid rocket propulsion system after the mounting module 210 is released from the propulsion module 250 and also after the payload 300 is deployed from the mounting module 210. Maintain 260.

In at least these and other examples, the weight of each of the solid fuel propellant 268, of the propulsion module 250, or of the vehicle 200 is between 20% and 50% of the total weight of the launch system 100. I can.

The propulsion module 250 further comprises a suitable steering system, including, for example, thrust vector control (TVC) devices, and/or aerodynamic steering via fins 215.

The sensor system 269 is coupled to the controller 270 to alert the controller 270 when a desired altitude and/or a predetermined range and/or time period T has been reached after firing of the launch system 100. It is composed. For example, sensor system 269 includes an accelerometer to enable controller 270 to determine when firing system 100 has slowed down and/or reached its apogee.

Optionally, vehicle 200, in particular propulsion module 250, is a suitable accelerometer coupled to controller 270, configured to alert controller 270 when firing system 100 transitions between deceleration and acceleration. 272).

Optionally, the vehicle 200, in particular the propulsion module 250, comprises a communication module 275 coupled to the controller 270. The communication module 275 is configured to enable communication between the ground station and the vehicle 200 by, for example, a direct radio link or a satellite link. For example, such communication may include telemetric communication and/or any other sensor information provided by sensors transported from vehicle 200 to ground station by payload 200 and/or at launch and/or It may include command signals from the ground station to the vehicle 200 for causing the vehicle 200 to perform various operations during its subsequent flight.

2, 3 and 4, at least in this example, the payload 300 is, in its containment configuration, an external containment geometrical envelope ES that allows the payload 300 to be received within the envelope E. Have. In other words, all parts of the payload 300 (when in the containment configuration) are accommodated within the envelope E, and will not cross this envelope E. The outer geometrical envelope ES of the payload 300 in the containment configuration has a diameter and length that does not exceed the diameter D1 and the length LE of the envelope E.

In particular, referring to FIG. 5, the payload 300 has, in its deployed configuration, an externally deployed geometric envelope ED that does not allow the payload 300 to be accommodated within the envelope E. In other words, at least some portions of the payload 300 (when in the deployed configuration) will traverse this envelope E.

In at least this example, the payload 300 is a UAV.

At least in this example the payload 300 is configured as a fixed wing vehicle, but in this and other examples of alternative variants the payload may be in the form of a paraglider or any electric glider. In yet another alternative variant of these and other examples, the payload may be or be in the form of a rotor vehicle, e.g. a helicopter, autogyro, onicopter, quadcopter, etc., and each onboard propulsion system is The payload is designed to provide vector-powered flight at subsonic cruising speeds.

As already mentioned, at least in this example, the payload 300 is an aerodynamic configuration that allows, at least in each deployed configuration, to be operated in an aerodynamic flight mode when the payload 300 is released from the vehicle 200. Have. As used herein, the term "aerodynamic flight mode" refers to the fact that the payload is in continuous flight, e.g., particularly in subsonic cruising conditions, by the payload 300, for example through aerodynamic floating surfaces. Including the operating modes of the payload 300 capable of aerodynamically powered flight, in which the floatation is provided in a manner.

In at least these and other examples, the lift-hang ratio of the payload 300 in the deployed configuration is at least 8, and may be greater than 9, 10, 11, 12, 13, 14, 15 or 15.

In at least this example, the payload 300 includes aerodynamic floating surfaces in the form of a fuselage 320 and a containable wing system 340.

In at least this example, the retractable wing system 340 is also in a tandem wing configuration, with a front wing set 360 and a tail wing set 380.

The front wing set 360 includes a front port wing 362 and a front starboard wing 364, each of which is hingedly mounted to the fuselage 320 at respective hinges (not shown) so that each wing is, respectively. From the storage position, the span of the wing of the fuselage 320 is nominally parallel to the longitudinal axis LA3 of the fuselage 320, the length of each wing is significantly non-parallel to the longitudinal axis LA3 of the fuselage 320, respectively. The deployment configuration set at the sweep angle of allows you to reversibly swing forward around each pivot axis.

In this example, the sweep angle is at or near nominal 0°.

In alternative variants of this and other examples, the wings of the front wing set are swept aft; For example, the sweep angle is greater than 0° but less than 45°. In yet other alternative variants of this and other examples, the wings of the front wing set are swept forward.

In at least this example, the front port wing 362 and the front starboard wing 364 are located on the upper portion of the fuselage 320, and the fuselage 320 includes the front port wing 362 and the front starboard wing 364. Includes an upper cutout 322 that provides a parking space for receiving at each storage location. Also, at least in this example, the front port wing 362 and the front starboard wing 364 are located at different heights on the upper portion of the fuselage 320, so that in the retracted position, as best seen in FIGS. 3 and 4 Likewise, one of the wings (port wing 362 in this example) is in an overlying relationship with the other wing (starboard wing 364 in this example).

The aft wing set 380 includes a trailing port wing 382 and a trailing starboard wing 384, each of which is hingedly mounted to the fuselage 320 at respective hinges (not shown) so that each wing is, respectively. The span of the wing of the fuselage 320 is from a storage position that is nominally parallel to the longitudinal axis LA3 of the fuselage 320, and the span of each wing is in a deployment configuration that is considerably non-parallel to the longitudinal axis LA3 of the fuselage 320, respectively. It is possible to swing reversibly in the aft direction around the pivot axis of, and to be set at each sweep angle. In this example, the sweep angle is nominally 0°. In alternative variants of this and other examples, the wings of the set of aft wings are aft swept; For example, the sweep angle is greater than 0° but less than 45°. In yet other alternative variants of this and other examples, the wings of the set of aft wings are swept forward.

In at least this example, the aft port wing 362 and the trailing starboard wing 364 are also located above and on the upper portion of the upper incision 322 of the fuselage 320 so that the aft wing set 380 is At each of the containment locations, it is possible to be accommodated in an overlying relationship with the front port wing 362 and the front starboard wing 364. Also, at least in this example, the aft port wing 364 and aft starboard wing 384 are located at different heights on the upper portion of the fuselage 320, so that in the retracted position, as best seen in FIGS. 3 and 4 Likewise, one of the wings (port wing 382 in this example) is in an overlying relationship with the other wing (starboard wing 384 in this example).

In alternative variations of this and/or other examples, the aft wing set 380 may instead include, for example, various sweep wings or angled wings.

In this example, the wings 382 and 384 of the aft wing set 380 have longer spans than the wings 362 and 364 of the front wing set 360.

In at least this example, the wings 382, 384 of the aft wing set 380 and the wings 362, 364 of the front wing set 360 are, for example, the payload 300 landing after the mission is over. After doing so, you can swing back to the original containment position. In this or other examples, the wings 382, 384 of the aft wing set 380, and the wings 362, 364 of the front wing set 360 are, for example, just before the payload 300 lands. It can swing back to its original containment position, for example between a height of several meters from the ground, for example between 1m and 10m.

In at least this example, each of the front wing set 360 and the rear wing set 380 is configured as the main lift generating wings of the payload 300. For example, the ratio of the lift generated by the front wing set 360 to the lift generated by the rear wing set 380 is 50:50, or alternatively 40:60, or alternatively 30:70, Or alternatively 60:40, or alternatively 70:30.

In alternative variations of these and other examples, an alternative configuration for the containable wing system 340 may be provided. For example, the front wing set 360 may instead be configured as canards, and the rear wing set 380 may be configured as the main lift generating wings of the payload 300.

In yet other alternative variations of this and other examples, the front wing set 360 may instead be configured as the main lift generating wings of the payload 300 and the rear wing set 380 is configured as a tail wing.

In either case, at least in this example, the payload 300 further includes port and starboard tail pins 390 for lateral stability and control. In this example, the tail pins 390 protrude downward from the intermediate height of the fuselage 320 for tail compaction, particularly as can be seen in FIG. 3. In at least this example, each tail pin 390 is hingedly mounted to the fuselage 320 at each hinge (not shown) so that each tail pin, the span of each pin is the longitudinal axis of the fuselage 320 From the storage position (FIG. 4) nominally parallel to LA3, the span of each pin is significantly non-parallel to the longitudinal axis LA3 of the fuselage 320 and at each sweep angle with respect to the longitudinal axis LA3. , For example, it is possible to swing reversibly in the aft direction around each of the pivot axes in a deployment configuration set to 90° (FIG. 5).

In at least this example, payload 300 is a powered aircraft and includes propulsion system 330. In this example, the propulsion system 330 includes a tractor propeller 332 driven by one or more electric motors, mounted in front of the fuselage 320 and coupled to suitable batteries. In alternative variations of these and other examples, the propulsion system 330 may additionally or alternatively include a pusher propeller driven by one or more electric motors. In yet another alternative variant of this and other examples, the propulsion system is, in addition or alternatively to electric motors, to drive one or more rotors, fuel combustion engines, for example one or more internal combustion engines or one It may include the above gas turbine engine. Such rotor(s) may include propellers 332 and/or may include more than one tractor propeller and/or more than one pusher propeller. In yet another alternative variant of this and other examples, the propulsion system may replace the propeller(s) with other thrust generating configurations, e.g. turbo jet engines, turbo fan engines, duct fan configurations, etc. have.

In examples where the propulsion system comprises more than one internal combustion engine, each such internal combustion engine may be coupled to a supercharger or turbocharger, for example to enable operation at high altitudes, for example at altitudes above 5 km. .

In at least some examples where the propulsion system 330 includes only one electric motor or more than one electric motor, such propulsion system may be the altitude desired by the payload 300 in the absence of the vehicle 200 (H), or It is important to note that at least it is not possible to achieve a sufficiently high rate of increase. For example, in this case, the propulsion system 330 is suitable for providing power for cruising at a desired altitude (H), but in the absence of the vehicle 200, it is used to propel the payload 300 to the desired altitude. If used, it can contain regular batteries that can deplete before reaching this altitude. Alternatively, for example, the propulsion system 330 is suitable for reaching the desired altitude H, but when the vehicle 200 is absent due to the weight of the battery, it is compared with the rate of ascent of the propulsion system 100. In this case, at a fairly low ascent rate;-In this case, the battery may become quite depleted and may not provide power for cruising for a significant period of time -, and may include high-load batteries capable of propelling the payload 300 to a desired high level. .

In at least this example, the propeller 332 is pivoted aft at a position close to the fuselage 320 to improve compactness, in the storage configuration of the payload 300, as shown in FIGS. 3 and 4 Includes propeller blades. For example, and particularly in the deployed configuration of the payload 300, when the propeller 332 is rotated by the engine, the propeller blades receive centrifugal force and pivot forward in a propulsion configuration (e.g., as shown in FIG. 5). And, the propeller wings are in a propulsion configuration at least until the payload 300 lands.

In alternative variants of these and other examples, the payload 300 is a non-powered vehicle, does not contain a propulsion system, and essentially operates as a glider.

In at least this example, payload 300 includes a suitable flight controller, navigation system and other suitable sensors (not shown).

It should be noted that in alternative variations of this example, and in other examples, the payload may include other configurations that allow each payload to be reversibly or irreversibly deployed from a respective containment configuration to a respective deployment configuration. do.

Optionally, the payload 300 includes a payload communication module (not shown) coupled to the flight controller. The payload communication module is configured to enable one-way or two-way communication between the ground station and the payload 300, for example by a direct radio link or a satellite link. For example, such communications may include telemetric communications and/or sensor information from payload 300 to a ground station and/or allow payload 300 to perform various actions at launch and during its subsequent flight. For example, it may include command signals from the ground station to the payload 300 for actively controlling the flight of the payload 300.

Optionally, the payload 300, in particular the flight controller, is configured to enable autonomous control of the payload 300, for example to perform a predetermined mission according to the mission parameters.

In at least this example, the payload 300 may be mission sensitive in at least some examples, and thus further comprises a payload (not shown) specifically adapted to perform the desired mission by the payload.

Referring particularly to FIG. 5, at least in this example, and in other examples, and according to another aspect of the present disclosure, the payload may include a sensor system 800 comprising one or more sensors 810 and Each sensor 810 is configured to detect and/or receive electromagnetic radiation in a predetermined wavelength range along a line of sight (LOS). For example, at least one of these sensors may be:

- The infrared (IR) sensor, and the predetermined wavelength range, includes portions or all of the IR wavelength range of the electromagnetic spectrum; And/or

- The ultraviolet (UV) sensor, and the predetermined wavelength range, includes portions or all of the UV wavelength range of the electromagnetic spectrum; And/or

- The optical sensor (eg, electro-optical sensor), and the predetermined wavelength range, includes portions or all of the visible wavelength range of the electromagnetic spectrum.

In addition, as shown in Figures 9 and 10, each sensor 810 points in a direction away from Earth at least when the payload 300 is in aerodynamic-powered flight, particularly at a predetermined altitude and at a design subsonic cruising speed. Each has its own LOS (via each aperture). In other words, LOS has a positive elevation (g) with respect to the horizon. The elevation (g) of the LOS may be in the range of 0° (horizontal, i.e. parallel to the horizon) to 90° (vertical, i.e. orthogonal to the horizon), and in at least some applications, the elevation (g) of the LOS is vertical. Or close to, for example the following ranges: 30° to 90°; 35° to 90°; 40° to 90°; 45° to 90°; 50° to 90°; 55° to 90°; 60° to 90°; 65° to 90°; 70° to 90°; 75° to 90°; 80° to 90°; 85° to 90°; It is within the range of any one of 88° to 90°.

In addition, for an elevation (g) other than 90°, each LOS has an azimuth angle (η). At least in this example, and in other examples, the azimuth angle η is defined for the payload 300, while in other examples the azimuth angle η may instead be defined for the Earth. In particular, the azimuth angle η may be defined with respect to the longitudinal axis LA3 of the payload 300 when the longitudinal axis LA3 is horizontal, that is, horizontal with respect to the earth. Accordingly: the azimuth angle η of 0° is in front parallel to the longitudinal axis LA3; The azimuth angle η of +180° or -180° is in the trailing direction parallel to the longitudinal axis LA3; The azimuth angle η of +90° is in the port side direction orthogonal to the longitudinal axis LA3; The azimuth angle η of -90° is in the direction of the starboard orthogonal to the longitudinal axis LA3.

In at least this example, and in other examples, the azimuth angle η is in a range between 0° and ±180° with respect to the longitudinal axis LA3 of the payload 300. In some examples, the azimuth angle η is in a range between +90° and +180° with respect to the longitudinal axis LA3 of the payload 300 and/or the azimuth angle η is the longitudinal axis of the payload 300 It is in the range between -90° and -180° for (LA3).

Each sensor 810 is mounted on the payload 300 in a manner that allows each LOS to point to a desired elevation (g) and azimuth (η). Referring again to FIG. 5, for example, at least in this and other examples, the one or more sensors 810 are the upper portion of the fuselage 320 so that the respective apertures of the sensors 810 are generally facing upwards. , For example located on the upper incision 322. One or more sensors 810 are fixedly mounted on the upper part of the fuselage 320, and accordingly, the elevation (g) and/or the azimuth angle (η) of the LOS can be adjusted by manipulating the payload 300, for example, of the fuselage. It can be changed by adjusting one or more of the angle of attack, the angle of attack, the yaw angle, the pitch angle, or the roll angle. Alternatively, one or more sensors 810 may be movably mounted to the fuselage, for example through a suitable gimbal mechanism that allows the LOS to be angularly displaced relative to the fuselage in 1, 2 or 3 degrees of freedom.

Alternatively, the one or more sensors 810 may be fixed or movable, while the respective apertures of the sensors 810 are generally facing upwards, and the other object to the fuselage 320, for example, an upper incision. It may be located at 322.

Each of the sensors 810 has a field of view (FOV) for the LOS. The FOV can be conceptualized for an imaginary cone where the LOS intersects the vertex of the cone and is orthogonal to the circular cross section of the cone, and has a half angle θ; FOV can be considered synonymous with this half angle (θ).

At least in this example, and in other examples, the FOV is, for example, less than 5°.

In some cases, the FOV is configured to be optimized to be able to detect and/or identify and/or track an object, for example along the LOS.

Such an object may generally be in a vertical direction above the position of the payload 300, and may also be displaced in a horizontal direction with respect to the payload 300.

Such objects may be, for example, orbital satellites, aircraft, or anti-aircraft missiles.

According to this aspect of the present disclosure, a payload comprising at least one sensor having a LOS having a positive elevation (g) relative to the horizon is provided with any suitable launch systems, for example some types of existing launch systems. Can be used to fire quickly and disengage at a desired altitude. In either case, another example of a launch system includes payloads and vehicles, wherein:

- The payload includes aerodynamically floating surfaces and an onboard propulsion system designed to provide aerodynamically powered flight at a design subsonic cruising speed to the payload at a desired altitude;

- The vehicle is configured to transport at least one payload, and further comprises a solid rocket propulsion system for propulsion of the launch system while transporting the at least one payload;

- The vehicle is configured to release the payload relative to the vehicle at a predetermined altitude;

- The at least one payload includes at least one sensor with a line of sight (LOS).

In at least this example, the payload 300 includes a vehicle recovery system (not shown) for recovering the vehicle after the mission has ended. For example, the vehicle retrieval system may include a parachute that allows the payload to make a soft landing after the mission is over; Optionally, when the parachute is deployed, the wing or part of the wings can be folded back into a containment configuration or partially containment configuration, or alternatively, the wings can come out. Alternatively, the vehicle recovery system may include a suitable undercarriage that allows the payload to perform a controlled horizontal landing on a runway or other suitable ground.

According to one aspect of the present disclosure, the launch system 100, in particular the controller 269, is the launch system 100 at predetermined conditions that enable the payload 300 to achieve aerodynamic flight in low subsonic cruising conditions. ) (Especially from the vehicle 200, in particular from the propulsion module 250). For example, these conditions may be between 50 m/s and 150 m/s, and/or less than 0.65 M, or less than 0.6 M, or less than 0.55 M, or less than 0.5 M, or less than 0.45 M, or less than 0.4 M, or 0.35 A Mach number (M) of less than M, or less than 0.35M, or less than 0.25M, or less than 0.2M.

According to this aspect of the present disclosure, the firing system 100, in particular the controller 269, is provided from the firing system 100 (especially transport) at a predetermined forward speed in which the payload 300 correlates with the respective subsonic cruising speed. It is configured to release the payload 300 from the sieve 200, in particular from the propulsion module 250). According to this aspect of the present disclosure, the predetermined forward speed is a subsonic speed, and may be in the range of zero to a maximum ±0.3 Mach number of the design subsonic cruising speed. Accordingly, for example, in the case of a subsonic cruising speed of 0.6M, the predetermined forward speed may be in a range of 0 to 0.3M and a maximum of 0 to 0.9M.

In the first embodiment of the example shown in FIGS. 1-5, the launch system 100 has a mass of about 1,000 Kg, the propulsion module 250 has a mass of about 500 Kg, and the mounting module 210 is about It has a mass of 500 kg. Referring to FIG. 1, this places, in at least one example, the center of gravity (CG) of the firing system 100 longitudinally closer to the trailing end 207 than to the nose 208.

It should be noted that in at least these and other examples, the payload 300 cannot itself reach the desired altitude H without the vehicle 200. For example, the payload 300 does not have a propulsion system capable of propelling the mounting module 300 at or close to a desired altitude (that is, excluding the vehicle 200 and its propulsion system), for example, the payload 300 ) There is no rocket motor system in itself capable of providing thrust for propulsion, or in fact there is no rocket motor system in the payload 300 itself.

For example, at least in this example, the onboard propulsion system is not capable of allowing the payload 300 to reach the desired altitude by itself.

For example, at least in this example, the onboard propulsion system may itself enable the payload 300 to reach the desired altitude H within a time period less than the critical time period from the launch point (LP). Or, the onboard propulsion system itself allows the payload 300 to reach the desired altitude H within a time period less than the critical time period from the launch point LP, and also any cruising of the payload 300. Or the prowl cannot be extended. In contrast, when transported by a vehicle in connection with the launch system 100, the payload 300 may reach a desired altitude H within a time period less than the critical time period. In other words, in at least this example, the rocket propulsion system comprises a solid propellant and at least one solid rocket motor configured to propel the launch system 100 including the payload 300 to a desired altitude H.

For example, the threshold time period can be within any of the following: 1 to 2 minutes, or 2 minutes, or 5 minutes, or 10 minutes, or 60 seconds, or 50 seconds, or 40 seconds, or 30 seconds.

Also, at least in this example, the launch system 100 is designed to reach a maximum velocity at an altitude below the desired altitude H, through the thrust generated by the vehicle 200, where this maximum velocity is the payload. The design of 300 is higher than the subsonic cruising speed. Also, at least in this example, the payload 300 cannot reach this maximum speed on its own without the carrier 200. For example, this maximum speed is at least 1.5 times the design subsonic cruising speed, or twice the design subsonic cruising speed, or 3 times the design subsonic cruising speed, or 4 times the design subsonic cruising speed, or the design subsonic cruising speed. 5 times, or more than 5 times the design subsonic cruising speed.

It should also be noted that, at least in this example, the payload 300 is configured to provide a first average rate of ascent in the absence of the vehicle 200, ie by itself and using only the payload propulsion system. On the other hand, the launch system 100 is designed to reach a second average ascent rate at an altitude below the desired altitude, in which case the second average ascent rate is greater than the first average ascent rate. These average rates of increase may include respective average rates of increase. At least in this example, the payload 300 cannot itself reach the second proven rate of rise. For example, the ratio of the second ascent rate to the first ascent rate may be any one of the following: 1.5, 2, 3, 4, 5, 6, 7, 8, 9, 10, or more than 10.

According to one aspect of the present disclosure, and referring to FIG. 6, a first example of a method for operating a launch system 100 collectively referred to as 1000 is provided, wherein the payload 300 is the launch system 100. The speed is fired at the desired altitude (H).

According to step 1100 of the method 1000, the launch system 100 operates the rocket motor 265 of the propulsion module 250, at an angle within a maximum of ±15° relative to the vertical, the launch point LP (Fig. 8). ) Is fired in the nominal vertical direction at the desired altitude (H). The launch system 100 is a flotation phase during a time period (ΔT) in which the mass of the launch system 100 simultaneously decreases as the rocket motor generates thrust (TH), the launch system 100 is accelerated, and fuel is consumed. (BP, boost phase) is passed. In at least this example, the speed reached by the launch system during the lifting phase BP may significantly exceed the cruising speed of the payload 300 or the maximum speed of the payload 300. Termination of the thrust by the rocket motor 265 terminates the flotation phase BP. In the flotation phase, the launch system 100 reaches altitude (HB).

For example, such a launch point (LP) may be a permanent launch facility (e.g., on land or water, e.g. at sea), or an electric launch platform (e.g., land) that allows the location of the launch point to move. And/or an award).

In step 1120 immediately after the period during which the rocket motor stops generating thrust (ΔT ), there is a deceleration phase (DC) in which the launch system 100 decelerates due to gravity and drag acting on the launch system 100. .

As an example, the launch system 100 has a mass of about 1,000 Kg, the propulsion module 250 has a mass of about 500 Kg, and the mounting module 210 has a mass of about 500 kg, of which about 425 Kg is a payload. Is the mass of 300. The rocket motor 265 has an ISP of about 200 seconds, providing a thrust TH of 34 KN for a period of 25 seconds (ΔT). In this example: the change in thrust over time is shown in Fig. 7A; The change in acceleration over time is shown in Fig. 7B; The change in mass over time is shown in Figure 7c; The change in height over time is shown in Fig. 7D.

During the deceleration phase DP, it is possible for the firing system 100 to continue raising the height DH past the altitude HB.

In particular, referring to FIG. 8, during the lift phase (BP) and the deceleration phase (DP), if the launch system 100 continues, a trajectory or pseudo-ballistic trajectory (TJ) that will bring the launch system 100 to the maximum altitude of the apex (MA). ) Followed by acceleration of the firing system 100 toward the ground G due to gravity. The speed of the launch system 100 at maximum altitude (MA) is within a range between the cruising speed of the payload 300 and zero (at maximum altitude MA).

At the desired altitude (H), which may be within the altitude (BH), or within the height (DH) beyond the altitude (BH), which may be or close to the maximum speed (MA), from the vehicle 200 to the payload 300 Separation begins.

In this example, this separation is performed by first disengaging the mounting module 210 from the propulsion module 250 in the disengagement stage NP of step 1130. For example, this separation may be accomplished through an explosion of explosive bolts holding interfaces 215 and 255 together, for example in response to an appropriate command via a controller, for example controller 270.

According to this aspect of the present disclosure, the disengagement stage NP of step 1130 occurs at a predetermined forward speed that correlates with each subsonic cruising speed of the payload 300. According to this aspect of the present disclosure, the predetermined forward speed is a subsonic speed, and may be in the range of zero to a maximum ±0.3 Mach number of the design subsonic cruising speed. Accordingly, for example, in the case of a subsonic cruising speed of 0.6M, the predetermined forward speed may be in a range of 0 to 0.3M and a maximum of 0 to 0.9M.

After step 1130, the mounting module 210 continues to step 1135, while at the same time the pushing module 250 is withdrawn in step 1138. In step 1138, the propulsion module 250 follows a general or nominal ballistic trajectory TJ2 towards the target area GT2. The target area GT2 may be designated as having no population and/or property, and accordingly, for example, the recovery of the propulsion module 250 through a gravity crash landing or a soft landing (for example, by parachute deployment) is a person or property Will be considered as not endangering. This target area GT2 may include, for example, predetermined locations in the sea or desert, or other unmanned areas, or, for example, a fenced "graveyard" area for this purpose. Can include.

In the disengagement stage (NP) of step 1130, the portion of the vehicle 200 containing the rocket propulsion system, i.e., the propulsion module 250 is subsonic, and the design subsonic cruising speed of the payload 300 is zero to maximum. It should be noted that it is separated from the payload 300 (and thus the payload 300 is coupled to the mounting module 210) at an advancing speed that can be in the range of ±0.3 Mach number.

The desired altitude (DH) in the trajectory (TJ) is selected so that the forward velocity (S) of the launch system 100 is within the desired velocity range and/or the dynamic pressure of the launch system 100 is within the desired dynamic pressure range. This will allow the payload 300 to reach subsonic aerodynamic flight at or below the design cruising speed. In at least one example, the desired altitude is also above the cloud base. For example, this forward speed (S) is 100 m/s or less. For example, the desired altitude may be about 10 km, and this altitude may be reached in at least about 40 seconds via the launch system 100 in the example described above. This forward speed is a subsonic speed, and may be within a range from zero to a maximum of ±0.3 Mach number of the design subsonic cruising speed. Accordingly, for example, in the case of a subsonic cruising speed of 0.6M, the predetermined forward speed may be in a range of 0 to 0.3M and a maximum of 0 to 0.9M.

In step 1135, the payload 300 is removed from the mounting module 210: the payload 300 continues to step 1140, while at the same time the empty mounting module 210 is retrieved in step 1148. In step 1148, the empty mounting module 210 follows the general or nominal ballistic trajectory TJ3 towards the target area GT3. The target area GT3 may be designated as having no population or property, and accordingly, the recovery of the empty mounting module 210 through, for example, a gravity crash landing or a soft landing (for example, by landing parachute deployment) is a person or property Will be considered as not endangering. This target area GT3 may include, for example, predetermined locations in the sea or desert, or other unmanned areas, or, for example, a fenced "graveyard" area for this purpose. Can include.

The target area GT3 may be the same as the target area GT2, or alternatively, the target area GT3 and the target area GT2 may be different from each other.

In step 1140, deployment step PP, the currently released payload 300 is operated to arrive at a deployed configuration. In the example shown in FIGS. 1 to 5, the front port wing 362 and the front starboard wing 364 of the front wing set 360 are pivoted from the front to the outside, and the trailing port wing of the rear wing set 360 ( 382 and aft starboard wing 384 are pivoted outward in the aft direction, and tail pins 390 are pivoted outwardly from downwards. The propeller 332 is radiated by the engine, and the propeller blades of the propeller 332 receive centrifugal force and are pivoted in a propulsion configuration from the front.

In a deployed configuration, and having an initial forward speed S within the aforementioned speed range, the payload 300 leads to low power subsonic aerodynamic flight. In at least such an example, the power low subsonic aerodynamic flight is between 50 m/s and 150 m/s, and/or less than 0.65M, or less than 0.6M, or less than 0.55M, or less than 0.5M, or less than 0.45M, or It runs at an air velocity of Mach number of less than 0.4M, or less than 0.35M, or less than 0.35M, or less than 0.25M, or less than 0.2M.

In step 1150, the payload 300 proceeds with the mission in the mission phase MP, and the mission has mission objectives that may be preset or set interactively through communication with a ground station. In carrying out the mission objectives, the payload 300 may roam or cruise at a desired altitude H, or may change this altitude in response to control signals provided by the flight controller, which may be preprogrammed. Or may include control signals provided by the ground station through the payload communication module.

Optionally, and depending on the nature of the mission and the mission targets, the payload 300 may provide mission data related to the mission targets and acquired during the mission to the ground base via the payload communication module. For example, such mission data may include sensor information acquired through sensors included in the payload 300.

Mission data may be associated with electromagnetic data acquired through one or more sensors 810, for example along each line of sight (LOS).

In step 1160, the mission is ended, and the payload 300 is recovered. Step 1160 may occur after the mission objectives have been realized, where the payload 300 may be flown to a target area GT designated for a controlled landing (in a propelled or non-powered state).

In at least some examples, step 1160 may include reversing the aforementioned deployment of payload 300, where payload 300 is reduced from a deployed configuration to a containment configuration, which is just prior to landing or accretion of payload 300. In, for example, it can be implemented within 2 to 10 meters from the landing surface.

In at least some examples, step 1160 may include dropping all or a portion of the aerodynamically floating surfaces of payload 300, which is immediately prior to landing or settling of payload 300, for example 2 from the landing surface. Can run within to 10 meters. In these cases, the payload 300 may have its aerodynamic floating surfaces-which in this example is the wings 382, 384 of the aft wing set 380, and the wings 362, 364 of the front wing set 360. )-Is configured to selectively drop all or part of. For example, some or all of the wings 382, 384 of the tail wing set 380 and the wings 362, 364 of the front wing set 360 are connected to the fuselage 320 via explosive bolts, This can optionally be activated to allow the respective wings to be dislodged from the fuselage 320.

Optionally, the payload 300 may include a self-destruction system (not shown) for detonating the payload 300 in certain situations, and operation of the self-destruction system in these situations may constitute step 1160. These situations may include, for example, cases where the payload is partially damaged or lacks fuel or propulsion energy and is expected to land on an undesired territory, in which case it is desirable that the payload does not fall into the undesired load. These situations may also include, for example, the case where the payload 300 is steered toward a target where it is desirable to be damaged or blasted through the self-destruction of the payload.

Such self-destruction systems can take many forms. For example, the self-destruction system may be in the form of commands to a flight controller to enable it to collide with the ground or target with maximum momentum along the flight path. Alternatively, the self-destruction system may include an explosive, and its explosion may cause the payload 300 to explode or severely damage.

In the following method claims, alphanumeric characters and Roman numerals used to designate claim steps are provided for convenience only and do not imply any particular order of performing the steps.

Finally, it should be noted that the word "comprising" as used throughout the appended claims is to be interpreted as meaning "including but not limited to".

While there have been examples presented and disclosed in accordance with the subject matter of the present disclosure, it will be understood that many changes may be made without departing from the spirit of the subject matter of the present disclosure.

Claims (50)

A launch system comprising a carrier vehicle and at least one payload vehicle,
The payload comprises a payload propulsion system and aerodynamic lift surfaces designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;
The vehicle is configured to transport the at least one payload to at least the desired altitude, further comprising a solid rocket propulsion system for propelling the launch system to the desired altitude;
The vehicle is configured to provide a predetermined advance velocity at the desired altitude, the predetermined advance velocity being correlated with the design subsonic cruising velocity;
The vehicle is configured to release the payload relative to the vehicle at the desired altitude and the predetermined forward speed;
The design subsonic cruising speed is less than 0.7 Mach number;
The target altitude is higher than 3 km, launch system. The firing system of claim 1, wherein the predetermined advance velocity is a subsonic velocity, and the predetermined advance velocity is between zero and ±0.3 Mach number of the maximum design subsonic cruising velocity. The method according to claim 1 or 2, wherein the payload is deployable between a stowed configuration and a deployed configuration, and the payload is in the containment configuration when transported by the transporter, and the Wherein the payload is deployed in the deployed configuration after release, the payload being designed for aerodynamic power flight at the design subsonic cruising speed when in the deployed configuration. 4. The mount propulsion according to any one of claims 1 to 3, wherein there is no rocket motor system in the payload, the onboard propulsion system is itself unable to allow the payload to reach the desired altitude, or the onboard propulsion The system itself is unable to allow the payload to reach the desired altitude within a time period of less than 60 seconds; Or the onboard propulsion system is unable to itself enable the payload to reach the desired altitude within a time period of less than 2 minutes. The firing system according to any one of the preceding claims, wherein the firing system is designed to reach a maximum speed below the desired altitude, wherein the maximum speed is higher than the design subsonic cruising speed. The method of any one of claims 1 to 5, wherein the payload is configured to provide a first average climb rate in the absence of the vehicle, and the launch system is configured to provide a second average climb rate below the desired altitude. Wherein the second average ascent rate is greater than the first average ascent rate. The method of claim 6, wherein the payload cannot reach the second average ascent rate by itself, and/or, the second average ascent rate is: at least twice the first average ascent rate; At least 5 times the first average rate of increase; At least 10 times the first average rate of increase; The firing system of any one of at least 20 times the first average ascent rate. 8. The method according to any one of the preceding claims, wherein the desired altitude is: at least 5 km; At least 10 km; Firing system, which may be any one of at least 12 km. 9. The method of any one of claims 1 to 8, wherein the design subsonic cruising speed is: 0.65M; 0.6M; 0.55M; 0.5M; 0.45M; 0.4M; The firing system that is less than any one of 0.35M, 0.3M, 0.25M, 0.2M. 10. The method of any one of claims 1 to 9, wherein the onboard propulsion system comprises at least one of a fuel combustion engine and an electric motor operably coupled to a rotor, and optionally the rotor is a propeller. That is, the firing system. The firing system of claim 10, wherein the rotor is a propeller, and the propeller comprises pivotable propeller blades reversibly pivotable between a propeller containment configuration and a propeller propulsion configuration. The method according to any one of claims 1 to 11, wherein the vehicle comprises a propulsion module comprising the solid rocket propulsion system, and a mounting module configured to transport the payload, wherein the propulsion module is in the mounting module. It is removably fastened, wherein the disengagement between the propulsion module and the mounting module enables the payload to be released from the mounting module at the desired altitude and the predetermined forward speed. 13. The launch system of claim 12, wherein the propulsion module is configured to withdraw in a first predetermined target area, and/or the mounting module is configured to withdraw in a second predetermined target area. The method according to any one of claims 1 to 13, wherein the transport body comprises a mounting bay configured to receive the payload, wherein the mounting bay mounts the payload at the desired altitude and the predetermined forward speed. A firing system that is openable to enable release from the bay. 15. The firing system of claim 14, wherein the vehicle is configured to withdraw at a third predetermined target area. The firing system according to any one of the preceding claims, wherein the predetermined forward speed is within a range between zero and the design subsonic cruising speed. The solid rocket propulsion system according to any one of claims 1 to 16, wherein the vehicle disengages the solid rocket propulsion system from the vehicle when releasing the payload relative to the vehicle at the desired altitude and the predetermined forward speed. A firing system that is configured not to release. The method of any one of claims 1 to 17, wherein the at least one payload comprises at least one sensor having a line of sight (LOS) having a positive elevation with respect to the horizon. That is, the firing system. 19. The firing system of claim 18, wherein the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°. 20. The firing system of claim 19, wherein the FOV is configured to enable at least one of detecting, identifying and tracking an object. 21. The launch system of claim 20, wherein the object is any one of satellites, aircraft, or anti-aircraft missiles. The method of any one of claims 18 to 21, wherein the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or a visible spectrum. Firing system. The firing system according to any one of claims 18 to 22, comprising an inertial platform, wherein the at least one sensor is mounted on the inertial platform. A launch system comprising a vehicle and at least one payload,
The payload includes aerodynamically floating surfaces and an onboard propulsion system designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;
The vehicle is configured to transport the at least one payload, the vehicle further comprising a solid rocket propulsion system for propelling the launch system while transporting the at least one payload;
The vehicle is configured to release the payload relative to the vehicle at a predetermined altitude;
Wherein the at least one payload comprises at least one sensor having a line of sight (LOS) having a positive elevation. 25. The firing system of claim 24, wherein the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°. 26. The firing system of claim 25, wherein the FOV is configured to enable at least one of detecting, identifying, and tracking an object. 27. The launch system of claim 26, wherein the object is any one of satellites, aircraft, or anti-aircraft missiles. The method of any one of claims 24-27, wherein the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or a visible spectrum. Firing system. 29. A firing system according to any one of claims 24-28, comprising an inertial platform, wherein the at least one sensor is mounted on the inertial platform. As a method for firing a payload at a desired high velocity,
(a) providing a launch system comprising the payload and the vehicle,
The payload comprises aerodynamically floating surfaces and an onboard propulsion system designed for aerodynamic power flight at a design subsonic cruising speed at a desired altitude;
-Said vehicle is configured to transport said at least one payload to at least said desired altitude, further comprising a solid rocket propulsion system for propulsion of said launch system to said desired altitude;
The vehicle is configured to provide a predetermined forward speed at the desired altitude, the predetermined forward speed being correlated with the design subsonic cruising speed;
-Said vehicle is configured to release said payload from said mounting bay at said desired altitude and said predetermined forward speed;
-The design subsonic speed is less than 0.7 Mach number;
-Providing the launch system, wherein the desired altitude is higher than 3 km;
(b) firing the firing system and causing the firing system to reach the desired altitude and the predetermined forward speed;
(c) releasing the payload from the vehicle at the desired altitude and the predetermined forward speed;
(d) causing the payload to achieve aerodynamic power flight at the design subsonic cruising speed at least at the desired altitude. 31. The method of claim 30, wherein the predetermined advance speed is a subsonic speed, and the predetermined advance speed is between zero and ±0.3 Mach number of the maximum design subsonic cruising speed. The step (d) of claim 30 or 31, wherein the payload is deployable between a storage configuration and a deployment configuration, and after the release in step (c), deploying the payload from the storage configuration to the deployed position (d) Wherein the payload is designed for the aerodynamic power flight at the design subsonic cruising speed when in the deployed configuration. 33. The method of any one of claims 30 to 32, wherein the desired altitude is: at least 5 km; At least 10 km; Firing system, which may be any one of at least 12 km. 34. The method of any of claims 30-33, wherein the design subsonic cruising speed is: 0.65M; 0.6M; 0.55M; 0.5M; 0.45M; 0.4M; The firing system that is less than any one of 0.35M, 0.3M, 0.25M, 0.2M. 35. The method of any one of claims 30 to 34, wherein the onboard propulsion system comprises at least one of a fuel combustion engine and an electric motor operably coupled to a rotor, wherein the rotor is a propeller, and the propeller is a propeller. And pivotable propeller blades reversibly pivotable between a containment configuration and a propeller propulsion configuration, the method comprising pivoting the propeller blades from the propeller containment configuration to the propeller propulsion configuration when the payload is in the deployed configuration. Comprising. 36. The method of any one of claims 30 to 35, wherein the vehicle comprises a propulsion module comprising the solid rocket propulsion system, and a mounting module configured to transport the payload, wherein the propulsion module is in the mounting module. Removably fastened, and step (c) includes disengaging the propulsion module with respect to the mounting module, and releasing the mounting body from the mounting module at the desired altitude and the predetermined forward speed thereafter. Comprising. The method of any one of claims 30 to 36, wherein the vehicle comprises an openable mounting bay configured to receive the payload, wherein step (c) comprises the steps of opening the mounting bay and the desired altitude and And releasing the payload from the mounting bay at the predetermined forward speed. 38. The method of any of claims 30-37, wherein the predetermined forward speed is between zero and the design subsonic cruising speed. 39. The method of any one of claims 30-38, further comprising step (h), wherein step (h) comprises:
-Reversing the deployment, wherein the payload is reduced from the deployment configuration to the containment configuration;
-Dropping the aerodynamic floating surfaces. 40. The method of claim 39, wherein step (h) is implemented just before the accretion of the payload on the ground at the end of the mission. 41. The method according to any one of claims 30 to 40, wherein no parachute is deployed with respect to the payload when or after the payload is released with respect to the vehicle. 42. The method of any of claims 30-41, wherein the at least one payload comprises at least one sensor with a line of sight (LOS) and further comprising aligning the LOS with a positive elevation. . 43. The method of claim 42, further comprising using the at least one sensor for at least one of detecting, identifying, and tracking an object. 44. The method of claim 43, wherein the object is any one of satellites, aircraft, or anti-aircraft missiles. The method of any one of claims 42-44, wherein the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or a visible spectrum. Way. As a method for firing a payload at a predetermined altitude,
(a) providing a launch system comprising the payload and the vehicle,
The payload comprises aerodynamically floating surfaces and an onboard propulsion system designed to provide the payload with aerodynamic power flight at a design subsonic cruising speed at a desired altitude;
The vehicle is configured to transport the at least one payload and further comprises a solid rocket propulsion system for propulsion of the launch system while transporting the at least one payload;
The vehicle is configured to release the payload relative to the vehicle at a predetermined altitude;
-Providing the firing system, wherein the at least one payload comprises at least one sensor with a line of sight (LOS);
(b) firing the firing system and bringing the firing system to the desired altitude;
(c) releasing the payload from the transport at the desired altitude;
(d) causing the payload to achieve aerodynamic power flight at the design subsonic cruising speed;
(e) aligning the LOS with a positive elevation. 47. The method of claim 46, wherein the at least one sensor has a field of view (FOV) for the LOS, wherein the FOV is less than 5°. 48. The method of claim 47, further comprising using the at least one sensor for at least one of detecting, identifying, and tracking an object. 49. The method of claim 48, wherein the object is any one of satellites, aircraft, or anti-aircraft missiles. The method of any one of claims 46-49, wherein the at least one sensor is configured to receive electromagnetic radiation in at least one of an infrared (IR) wavelength, an ultraviolet (UV) wavelength, or a visible spectrum. Way.

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